From what Im told, its reasonable to have the grid extend out in all directions roughly fifteen times the chord length. Low Reynolds number simulations are performed with the Laminar Flow interface, while high Reynolds number simulations use the Spalart-Allmaras turbulence model, which has been specifically developed for airfoil design simulations. Im using MATLAB for generating the grid and other calculations. When you enter the fluid flow's Reynolds number into the simulation app, the appropriate fluid flow interfaces and meshes are automatically chosen based on this number. It can be used to visualize how changes to the airfoil thickness, camber, and chord length affect the aerodynamics. Being a function, the airfoil generator can be called several times from a loop to generate any number of airfoil data files.
The NACA Airfoil Optimization application computes the two main aerodynamic properties (the lift and drag coefficients) of a fully parameterized NACA airfoil. 'naca4gen.m' Generates the NACA 4 digit airfoil coordinates with desired no. You will have to calculate the following, Drag co-efficient Vs Angle of Attack Lift co-efficient vs Angle of Attack Compare the effect of turbulence models on the above two results. The aerodynamic properties of a wing, propeller, or turbine blade are to a large extent determined by the precise shape of the airfoil that is used. Given Problem:- Simulate flow over a 4 digit airfoil i.e NACA 2412 Airfoil.